Aircraft manufacturers face pressure to reduce weight, fuel consumption, and operating costs while meeting structural performance requirements. Consequently, manufacturers evaluating carbon fiber in aerospace industry applications must consider production costs, inspection needs, and certification requirements. Spacecraft programs face similar pressure because launch costs depend on mass.
Carbon fiber composites let engineers position reinforcement along structural loads and integrate components that would otherwise remain separate. However, resin selection, production consistency, and repair requirements influence whether those advantages justify the material choice.
This article explains carbon fiber's material properties, aerospace grades, and applications across aircraft and spacecraft. It also examines manufacturing, inspection, and lifecycle trade-offs that teams should compare before committing to a material system.
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The definition
What is carbon fiber in the aerospace industry?
Carbon fiber consists of slender filaments with carbon atoms ordered into elongated crystalline structures. Most aerospace fiber begins as polyacrylonitrile (PAN), although pitch provides another precursor. Processing involves stabilization near 392 to 572°F (200 to 300°C), carbonization at 1,832 to 2,732°F (1,000 to 1,500°C), and optional graphitization above 3,632°F (2,000°C). Aircraft generally use carbon fiber reinforced polymer (CFRP), where fibers bear loads while resin secures them and transfers forces between fibers.
Aircraft reinforcement includes unidirectional tape and woven fabric, while prepreg contains resin incorporated before component layup. Aerospace-grade CFRP requires rigorous testing and qualification of the complete material system for flight loads, temperature variations, and prolonged service. By comparison, carbon-carbon uses a carbon matrix instead of resin and serves high-temperature applications up to approximately 1,832°F (1,000°C). These material distinctions provide the basis for examining why engineers choose carbon fiber for weight savings, durability, and structural design flexibility.
Why it matters
Why aerospace engineers turn to carbon fiber
Reducing structural mass can improve fuel consumption, payload, and range while lowering operating costs. Weight is one of several levers covered in our review of technologies for improving aircraft fuel efficiency. However, teams need to compare complete components rather than select materials from fiber specifications alone. The following benefits and property comparison explain where carbon fiber merits further testing.
Strength and stiffness per pound
PAN-based fiber offers higher tensile strength and stiffness at lower density than the metal values compared below. However, engineers must use qualified laminate properties when calculating structural weight savings.
Fatigue resistance
A 2025 review by Mamat et al. reports epoxy CFRP retaining approximately 90 to 95% of tensile strength after one million loading cycles. Its corresponding figure for aluminum 7075-T6 is about 60%, making fatigue behavior an important comparison alongside static strength.
Corrosion resistance
CFRP avoids aluminum-type corrosion, which can reduce maintenance requirements over a component's service life. However, teams still need inspection plans for damage within the composite structure.
Reinforcement along load paths
Engineers can orient fibers to carry loads in selected directions, whereas metals generally have more uniform directional properties. Consequently, teams should compare layup options against the component's actual loading requirements.
Integrated structures
Boeing estimated a roughly 19-to-1 reduction in part count where composites replaced aluminum on the 787. Fewer separate components can reduce fastening requirements, although engineers must assess the complete structural design.
| Material | Approximate density | Approximate tensile strength | Approximate elastic modulus |
|---|---|---|---|
| Aluminum alloy | 0.0975 lb/in³ (2.70 g/cm³) | 65,300 psi (0.45 GPa) | 10.2 million psi (70 GPa) |
| Titanium alloy | 0.1626 lb/in³ (4.50 g/cm³) | 130,500 psi (0.90 GPa) | 16.0 million psi (110 GPa) |
| PAN-based carbon fiber | 0.0650 lb/in³ (1.80 g/cm³) | 725,200 psi (5.0 GPa) | 36.3 million psi (250 GPa) |
Interactive · Material comparison
Compare strength, stiffness, and density
Fiber value, before resin, layup and fiber fraction are applied.
How to read thisBars compare the selected table property using individual carbon fiber values rather than finished laminate properties, with strength per unit density calculated from the table values. Source values: Mamat et al., 2025 review.
The carbon fiber values describe individual fibers, while finished laminate properties depend on resin, layup, and fiber fraction. Mamat et al.'s 2025 review reports weight savings of 30 to 50% and fuel savings of 20 to 25%, depending on the component and comparison baseline. Therefore, teams must examine how aerospace-grade material systems differ from industrial alternatives before selecting materials or production processes.
Material grades
What separates aerospace-grade carbon fiber from industrial grades
Aerospace suitability depends on documented performance across the material system and manufacturing process, beyond a fiber grade label. The distinctions below connect fiber properties, resin selection, and qualification evidence with practical sourcing and production decisions.
Fiber grade and the stiffness-strength trade-off
Standard and intermediate modulus PAN fibers meet different stiffness requirements, so grade selection starts with component loads. Mamat et al.'s 2025 review lists standard-grade moduli around 33.4 to 36.3 million psi (230 to 250 GPa). Intermediate grades reach approximately 43.5 to 50.8 million psi (300 to 350 GPa), requiring comparison against the structure's stiffness targets.
Pitch-based high modulus carbon fiber reaches approximately 72.5 to 101.5 million psi (500 to 700 GPa) in that review. However, its reported elongation is just 0.3 to 0.5%, compared with 1.8 to 2.0% for standard-modulus PAN fiber. Therefore, engineers should assess stiffness alongside tensile strength and strain capacity rather than assume higher modulus means better overall performance.
Toughened epoxies and high-performance thermoplastics
Toughened epoxy systems support major aircraft structures, including the Boeing 787's Toray 3900-2 prepreg with T800 intermediate-modulus fiber. Industrial composites may instead use polyester or vinyl ester resins, creating different material systems that require separate evaluation. Automotive programs face a similar grade and cost choice, as our article on automotive lightweight composites describes. Consequently, teams should compare fiber-resin performance rather than treat similarly labeled fibers as interchangeable.
High-performance thermoplastics such as PAEK and PEEK provide alternatives, including the option to weld components during assembly. Meanwhile, Mamat et al.'s 2025 review gives epoxy CFRP an approximate service limit of 302°F (150°C). Engineers must validate the selected resin under relevant temperature and moisture conditions before choosing a matrix or joining process.
Prepreg, material allowables, and traceability
Prepreg provides a controlled fiber-to-resin ratio, but aerospace qualification extends beyond that starting material. It covers fiber surface treatment, sizing, resin, layup, cure conditions, inspection, and the data supporting structural design limits. Therefore, teams should request evidence for the complete qualified system rather than rely on a fiber supplier's specification sheet.
Traceability should connect the selected materials and production conditions with the evidence supporting their qualification. Shared thermoplastic allowables databases can shorten certification work, although teams must establish whether those data apply to their selected system. Procurement reviews should therefore examine material records, process controls, inspection requirements, and applicable certification data together.
Adoption path
How carbon fiber moved from fairings to fuselages
Carbon fiber moved from secondary parts into primary structures as manufacturers qualified materials and production processes. Testing for each application determined how quickly manufacturers could expand its use. The milestones below trace that progression in aircraft that still use aluminum, titanium, and steel for joints, landing gear attachments, and large forgings.
RB211 Hyfil blade testing
The Rolls-Royce RB211 program returned to titanium after its Hyfil carbon fiber fan blades failed bird-strike requirements. This outcome shows why engineers must validate impact performance alongside strength and weight.
Composites enter secondary structures
Manufacturers used composites in fairings, floor beams, access panels, and control surfaces such as spoilers, elevators, and rudders. These parts gave manufacturers practical experience before they adopted composites in primary load-bearing structures.
Certified Boeing 777 tail structure
Boeing used certified carbon fiber prepreg in primary tail components on the 777. Composites account for about 12% of the aircraft's weight, reflecting their selective use.
GE90 composite fan blades
The GE90 became the first commercial jet engine to use polymer composite fan blades. It replaced titanium blades with 22 composite blades.
GEnx blades and containment
The GEnx added a composite fan blade. It also used composite material for the fan containment case.
Boeing 787 enters service
The Boeing 787 entered service with CFRP wings and fuselage. Composites account for about half of the aircraft's structural weight.
Airbus A350 expands CFRP use
The Airbus A350 confirmed substantial CFRP use, and a 2025 review by Mamat et al. reports that composites account for more than 50% by weight on both the A350 and 787. Teams should verify how each percentage was measured before comparing the aircraft.
Welded thermoplastic fuselage demonstrator
The Airbus-led Clean Sky 2 Multifunctional Fuselage Demonstrator used a welded thermoplastic fuselage section. The project won a JEC Composites Innovation Award.
Composite fan blade flight hours
GE Aerospace reported operating experience with composite fan blades. Those blades had accumulated more than 300 million flight hours.
Applications
The role of carbon fiber in aircraft and spacecraft applications
Carbon fiber's value depends on the component's loads, operating conditions, production requirements, and maintenance obligations. Therefore, aerospace teams must evaluate weight savings alongside the complete structure's performance and cost. The following applications show where those comparisons matter most.
Interactive · Aircraft applications
Where carbon fiber earns its place
Select an aircraft zone to examine its application, supporting figures, and material selection considerations.
Spar weight savings up to 60%
Mamat et al. (2025) estimateCFRP reinforcement orientation allows engineers to adjust wing stiffness along structural loads.
Teams should compare complete assemblies, including joints, manufacturing requirements, and qualified laminate properties.
1. Wings and wing boxes
CFRP prepreg is used in Boeing 787 wings, where reinforcement orientation allows engineers to control structural stiffness. This directional design makes the laminate schedule an essential part of wing and wing box evaluation.
A 2025 review by Mamat et al. estimates wing spar weight reductions of up to 60% against metal alternatives. However, teams should compare complete assemblies, including joints and manufacturing requirements, before applying that estimate to another design.
2. Fuselage barrels and panels
The Boeing 787's composite fuselage barrels incorporate stiffeners during molding, integrating reinforcement into larger structural sections. A 2025 review by Mamat et al. estimates approximately 20% lower structural weight for these barrels compared with aluminum.
Composite fuselages also avoid aluminum-type corrosion, which can reduce maintenance requirements. Consequently, teams should compare structural integration and corrosion benefits against inspection access, impact damage assessment, and repair requirements.
3. Tail sections and stabilizers
The Boeing 777's certified CFRP prepreg tail structure illustrates carbon fiber's role in primary load-bearing components. Fiber orientation gives engineers a means of adjusting stiffness to meet the tail structure's loading requirements.
However, performance depends on the selected resin, reinforcement arrangement, and manufacturing controls throughout the component. Teams should compare qualified laminate properties, fatigue behavior, and inspection requirements when evaluating tail sections and stabilizers.
4. Control surfaces, fairings and other secondary structures
Carbon fiber composites are used in spoilers, rudders, elevators, fairings, and access panels. Across these components, engineers can position reinforcement according to the loads each structure must carry.
However, reducing component weight introduces material, tooling, inspection, and repair considerations that affect the overall business case. Teams should compare mass savings with production volume and maintenance requirements for each control surface, fairing, or panel.
5. Engine fan blades and containment cases
Engine applications require materials that meet demanding impact requirements alongside weight and structural targets. Hotter engine sections rely on other material families, covered in our piece on high-temperature materials for jet engines. In 1995, the GE90 became the first commercial jet engine to use polymer composite fan blades, replacing titanium with 22 composite blades. The GE9X uses 16 composite blades within a 134-inch fan.
The GEnx and CFM LEAP use composite fan blades and composite containment cases, extending the application beyond blades alone. In March 2026, GE Aerospace reported more than 300 million accumulated flight hours for composite fan blades.
However, bird-strike testing remains a material selection gate, as the RB211 blade experience illustrates. Teams should examine blade impact performance, containment requirements, and qualification evidence for each selected material system.
6. Cabin interiors and floor structures
Carbon fiber applications inside aircraft include seat frames, cabin dividers, and floor beams. A 2025 review by Mamat et al. estimates mass reductions of up to 30% for A350 seat frames and dividers.
However, glass fiber can offer a lower-cost option for interior parts with less demanding structural requirements. Teams should compare the value of weight savings against material expense, manufacturing requirements, and suitable glass fiber alternatives.
7. Helicopter rotor blades and airframes
Helicopter applications include rotor blades, tail structures, doors, seats, and instrument enclosures. These components present different load requirements, making reinforcement direction and qualified material properties central to selection.
Fatigue resistance offers a reason to consider CFRP, while impact damage still requires an appropriate inspection strategy. Consequently, teams should compare fatigue data, damage assessment methods, and repair provisions for each rotor or airframe component.
8. Uncrewed aircraft and drones
Military and commercial drones use carbon fiber to reduce structural mass in support of flight endurance. However, the value of that reduction depends on the aircraft's performance objectives and the finished composite structure.
Specialized molds and fixtures can make low-volume production expensive, even when reduced mass supports endurance targets. Teams should therefore compare endurance benefits with tooling investment, manufacturing consistency, and inspection requirements before selecting the material system.
9. Spacecraft, satellites and pressure vessels
Space applications include satellite panels, antenna reflectors, and structures that support payloads. Pitch-based high modulus fiber suits dimensional stability requirements, making stiffness and strain capacity important material selection criteria.
Heat shields and rocket nozzles require a separate evaluation of thermal performance and matrix chemistry. Carbon-carbon composites serve high-temperature applications up to approximately 1,832°F (1,000°C), according to the 2025 review by Mamat et al.
Composite overwrapped pressure vessels use a metal or plastic liner reinforced by an external fiber composite wrap to contain gases or propellants. NASA NESC identifies stress rupture and liner cracking as concerns because vessel failure can be catastrophic. Therefore, teams should examine stress rupture evidence, liner inspection methods, and the qualified vessel system before selection.
Production
How aerospace carbon fiber parts are made and inspected
Manufacturing quality determines whether a composite component achieves the properties established during material qualification. Consequently, teams must evaluate production controls and inspection capability alongside fiber and resin selection. The following processes explain how manufacturers build parts and verify their quality.
Prepreg layup and autoclave curing
Prepreg remains under controlled storage conditions before cutting and placement according to the specified fiber orientation schedule. The laid-up material is vacuum bagged and debulked before autoclave curing under heat and pressure. These operations help control void formation within the laminate.
After curing, manufacturers trim and drill the component before inspecting the finished structure. Therefore, teams should verify that storage, layup, cure, and finishing controls match the processes supporting the material's qualification.
Automated fiber placement and tape laying
Automated fiber placement, or AFP, deposits narrow prepreg tows along programmed paths suited to complex curved surfaces. Automated tape laying, or ATL, uses wider tapes for larger components with flatter geometries. Consequently, equipment selection should reflect the component's shape and reinforcement requirements.
AFP requires control of gaps, overlaps, wrinkles, and limits on how sharply fibers can follow curved paths. Teams should validate deposition quality on the intended geometry and confirm how manufacturing defects will be inspected and assessed.
Out-of-autoclave and thermoplastic processes
Resin transfer molding, resin infusion, and vacuum bagging offer alternatives to autoclave processing. Printed parts are another route, which our white paper on additive manufacturing in aerospace and defense examines. These routes can lower costs, although manufacturers must maintain tight process controls to limit voids. Thermoplastic CFRP also permits welded joints, giving teams another assembly method to evaluate.
Fraunhofer IFAM reports that the Airbus-led Clean Sky 2 Multifunctional Fuselage Demonstrator used CO₂ laser and ultrasonic welding. The project reported 10% reductions in weight and production cost, receiving a JEC Composites Innovation Award during January 2025. However, teams should validate those demonstrator results against their component geometry, production requirements, and qualified joining processes.
Non-destructive inspection
Ultrasonic testing is a principal inspection method for aerospace CFRP, supporting assessment of the component's internal condition. Other methods include tap testing, thermography, X-ray inspection, shearography, and computed tomography.
Teams should match inspection methods to component geometry, available access, and the defects or damage being assessed. Therefore, inspection capability should be evaluated alongside layup and curing requirements before committing to a production route.
Surface protection
Surface finishing, paint and lightning protection on composite skins
Composite skin selection must account for the layers that prepare, protect, and finish the structural laminate. These layers affect finished weight, repainting, and repair requirements. The following considerations connect surface preparation with environmental exposure and lightning protection.
Surfacing films and paint preparation
Epoxy surfacing films fill small holes and surface cavities, reducing the filling and sanding needed before priming and painting. Therefore, teams should evaluate surface quality alongside the labor required to prepare each component.
Aircraft undergo repeated repainting during service, so surfacing films must tolerate the chemicals used to remove paint. Teams should confirm compatibility between the film, paint system, and planned stripping process before approving the finished skin.
UV exposure before painting
Sufficient ultraviolet exposure can discolor and degrade epoxy, including before the protective finish is applied. Outdoor storage and exposure under factory lighting therefore deserve consideration during production planning.
Teams should review the exposure conditions between component manufacture and painting, including storage locations and lighting. Validation should establish whether those conditions affect the selected surfacing film or the quality of subsequent finishing.
Lightning strike protection layers
Expanded copper or aluminum mesh or foil can be incorporated into surfacing film to conduct lightning current away. Film and metal layer weights vary according to the aircraft's lightning strike zones.
Consequently, finished-skin weight comparisons should include surfacing film, conductive metal, primer, and paint alongside the structural laminate. Teams should also plan how repairs restore the lightning protection mesh within the affected area.
Fire behavior
How carbon fiber airframes behave in a fire
Composite fire performance depends on the resin, laminate construction, and location within the aircraft. Consequently, results from one tested configuration require careful interpretation before supporting another design. The following distinctions explain combustion behavior, burnthrough requirements, and the evidence teams should obtain.
What burns and what does not
Epoxy resin can decompose and burn, while residual carbon reinforcement forms a char layer that slows heating below the surface. Constantine Sarkos's May 2011 FAA Technical Center report, DOT/FAA/AR-TN11/8, describes a declining burning rate as this protection develops. In small-flame tests, burning remained confined to flame contact and stopped after the flame was withdrawn.
In one small-scale test configuration, decomposition affected seven plies within a 13-ply laminate. The report also recorded lower gas emissions than two burnthrough-resistant insulation materials, while full-scale testing demonstrated strong burnthrough resistance during a five-minute jet fuel fire. However, teams should retain those test conditions when interpreting the results, particularly when comparing emissions or laminate thicknesses.
Post-crash burnthrough and fuel tank requirements
FAA research associated delaying fuselage burnthrough for approximately five minutes with improved survivability, with limited additional benefit from longer delays. The FAA's April 9, 2007 proposed special condition addressed the absence of a composite wing and fuel tank skin standard for post-crash fires. It called for at least five minutes of resistance to an external fuel-fed pool fire, addressing tank flammability, burnthrough, remaining wing strength, and auto-ignition.
Sun-heated composite wing tanks showed greater ground flammability than aluminum tanks, although both cooled rapidly under flight conditions. The Boeing 787 uses an onboard tank inerting system as part of its fire protection. Its certification required fire safety comparable to conventional aluminum aircraft, making the complete tank and protection system central to assessment.
What teams should check
Fire testing should address the selected resin system, laminate construction, and intended location within the aircraft. Teams should plan evidence covering flame behavior, smoke, and burnthrough resistance under conditions relevant to that application.
A different resin, laminate, or installation should receive its own assessment of the evidence needed for qualification. Consequently, teams should verify that test reports represent the proposed configuration before using them to support design or certification decisions.
What gets in the way
The trade-offs aerospace teams need to plan for
Structural weight savings must justify the costs and obligations associated with manufacturing, inspection, maintenance, and disposal. Therefore, material selection requires a lifecycle assessment rather than a comparison of fiber properties alone. The following trade-offs identify what teams should evaluate before committing to CFRP.
Material and tooling cost
A 2025 review by Mamat et al. places aerospace-grade fiber at more than $20 to $25 per kilogram, compared with $2 to $4 per kilogram for aluminum alloys. Specialized molds and fixtures add expense, making production volume an important factor when comparing component costs.
Hidden impact damage and inspection burden
Impacts can cause internal delamination, resin cracking, and reduced compression strength even when the exterior appears intact. Consequently, teams should evaluate inspection access and damage assessment requirements alongside structural performance.
Lightning strike protection
The surface finishing section explains the protection layers used on composite skins. Teams should include these layers in finished-skin weight comparisons.
Temperature and moisture limits
Mamat et al.'s 2025 review gives epoxy CFRP an approximate service limit of 302°F (150°C). However, teams must validate the selected resin through hot-wet testing that reflects the component's operating conditions.
Repair complexity
Repair options include bonded patches, scarf repairs, bolted repairs, and replacement, depending on the component and damage. Each option requires appropriate surface preparation, cure control, and inspection, which teams should include in maintenance planning.
Certification time and data
FAA AC 20-107B, issued September 8, 2009, describes an acceptable compliance route for composite structural design, manufacturing, and maintenance. Teams should assess the necessary qualification data against applicable requirements, including EASA AMC 20-29 for relevant programs.
End-of-life recycling
Mamat et al.'s 2025 review reports pyrolysis fiber recovery reaching approximately 90 to 95% at 752 to 1,112°F (400 to 600°C). Separately, reported tensile strength retention is 80 to 90% after solvolysis or supercritical recycling and 50 to 60% after grinding, so recovered quantity and retained properties require separate comparisons.
Interactive · Component screener
Is this component a candidate for CFRP?
Answer all four questions for one component and its intended service conditions.
Prioritize further CFRP evaluation
Teams should compare manufacturing, inspection, repair, and end-of-life costs alongside the operating benefits of lower structural weight. Sourcing decisions must then establish which suppliers are qualified, what backup options exist, and how long requalification could take.
Supply chain
Sourcing and qualifying aerospace carbon fiber
Aerospace carbon fiber availability depends on qualified material and production sources, alongside manufacturers' stated capacity. Therefore, purchasing decisions must account for qualification constraints, precursor supply, and contract terms. The following considerations explain how supply concentration and approval requirements affect sourcing flexibility.
A concentrated supply base
CompositesWorld reported in 2020 that Toray held approximately 62,800 short tons (57,000 metric tons) of nameplate capacity in 2019. The reported global total was about 177,700 short tons (161,200 metric tons), indicating substantial capacity within one supplier.
Hexcel and Mitsubishi Chemical each held approximately 17,600 short tons (16,000 metric tons), according to the same assessment. Teijin held about 15,400 short tons (14,000 metric tons), while SGL Carbon held about 14,300 short tons (13,000 metric tons). However, teams should distinguish these dated nameplate figures from capacity qualified for a particular aerospace material system.
Why qualified sources are hard to switch
Hexcel's 2020 annual report explains that aerospace customers generally determine carbon fiber sources through their qualification requirements. It also describes qualification expense as a constraint on maintaining multiple suppliers, with some materials having just one or two approved sources.
The report states that an additional production line can require up to one year to obtain aerospace certification. It also explains that multi-year aerospace agreements often allocate a percentage of customer requirements instead of specifying fixed purchase volumes. Consequently, teams should examine qualification timing and contractual allocation together when assessing supply flexibility.
What teams should check
Hexcel's 2020 annual report identifies acrylonitrile as the input used to make PAN, connecting precursor availability with fiber sourcing. Teams should therefore ask about precursor supply, aerospace-qualified production capacity, and notification requirements for material or process changes.
A sourcing assessment should map qualified suppliers for each material system, credible backup options, and the time needed for requalification. Teams should compare those constraints with production schedules before treating an alternative supplier or additional line as available capacity.
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How we help
How can Prescouter help?
Selecting aerospace composites requires evidence across materials, manufacturing, suppliers, maintenance, and certification. We can help your team compare options and identify assumptions that need further testing. The following capabilities support decisions from early material evaluation through qualification planning.
Technology Scouting
Our Technology Scouting team compares fiber grades, resin chemistries, thermoplastic processing, and manufacturing routes that avoid autoclave curing. Options are assessed against your team's component loads, production volumes, and qualification requirements.
Our research can also examine surfacing films, lightning protection materials, and available recycling methods. We help your team identify candidates for testing and questions that remain unresolved before a material or process is selected.
Supplier and Partner Vetting
With Supplier and Partner Vetting, we identify fiber producers, prepreg suppliers, fabricators, and inspection partners for your team's intended application. Assessments examine qualification records, manufacturing controls, relevant capacity, and evidence supporting technical claims.
We can investigate precursor availability, alternative sources, and the qualification constraints affecting supplier changes. These comparisons help your team distinguish stated production capacity from supply that is qualified for the selected material system.
Expert & Customer Interviews
We run structured Expert & Customer Interviews with composite engineers, certification specialists, manufacturers, and maintenance, repair, and overhaul professionals. Conversations test assumptions about damage tolerance, repair requirements, fire testing, and achievable production rates.
We compare interview findings with technical documentation to identify agreement, uncertainty, and questions requiring physical validation. Your team can use those findings to refine test priorities and assess whether proposed manufacturing or maintenance assumptions are credible.
Regulatory Landscapes
Our Regulatory Landscapes service tracks FAA and EASA composite guidance, including AC 20-107B and AMC 20-29, alongside relevant special conditions. The research connects structural, fire, and flammability requirements with your team's intended material system and component location.
We help your team identify the documentation and testing questions that need resolution during qualification planning. This work can inform discussions with certification specialists and support comparisons between candidate materials, processes, and suppliers.
Common questions
FAQs
Do commercial airplanes use carbon fiber?
Yes, commercial aircraft use carbon fiber composites in structures such as wings, fuselages, and tails. A 2025 review by Mamat et al. reports composite shares above 50% by weight for the Boeing 787 and Airbus A350. The Boeing 777's reported composite share is approximately 12% by weight, although these figures describe total composite content.
Does NASA use carbon fiber in spacecraft?
Yes, NASA NESC examines composite overwrapped pressure vessels used aboard spacecraft and launch vehicles. Its work includes the interim cryogenic propulsion stage used for Artemis I. SMI Composites also reports carbon fiber use in Orion heat shield and nozzle hardware.
When did aircraft begin adopting carbon fiber?
An industry history traces aviation research interest in carbon fiber to the 1950s and 1960s. The RB211 Hyfil fan blade program followed around 1970, with secondary structural applications developing through the 1970s and 1980s. Later uses included certified primary tail structure on the Boeing 777 and wing and fuselage structures on the 787, which entered service in 2011.
Can carbon fiber composites burn?
Yes, the epoxy matrix can burn, while residual carbon reinforcement forms a char layer that slows heating beneath the surface. The FAA's May 2011 report, DOT/FAA/AR-TN11/8, describes small-flame tests in which burning stopped after the external flame was withdrawn. However, that behavior applies to the tested conditions and does not establish fire performance for every composite configuration.
Can aircraft carbon fiber be recycled?
Yes, a 2025 review by Mamat et al. reports pyrolysis recovering approximately 90 to 95% of fiber. It also reports tensile strength retention of 80 to 90% after solvolysis or supercritical recycling, compared with 50 to 60% after mechanical grinding. Teams should distinguish recovered fiber quantity from retained properties when evaluating subsequent uses.
Which carbon fiber producer leads by capacity?
Toray led the 2019 nameplate capacity figures reported by CompositesWorld in 2020. Its capacity was approximately 62,800 short tons (57,000 metric tons), against a global total near 177,700 short tons (161,200 metric tons). However, nameplate capacity does not establish whether a particular material or production line holds the necessary aerospace qualification.
